论文部分内容阅读
在预测子弹在超音速气流中靠近母弹的空气动力学特性研究中,采用了两个子弹分离计算机程序。这两个程序中的母弹干扰流场都根据分别代表体积和攻角效应的线性变化源/汇和偶极子分布计算。考虑到母弹存在弓形激波,计算的母弹流场中包含有一个非线性修正量。使用当量流场方法逼近具有敞开舱室的母弹。为了获得子弹上的负载,使用了在等级上较低的和中等方法计算。在一个程序的低级方法中,在有母弹流场时,子弹的气动力和力矩使用细长体理论计算。在另一个程序的中级方法中,子弹用分布在弹体轴上的直线奇点或板块法模拟,把表面压力分布进行积分就获得了子弹上的负载。其中包括了反射激波影响。在两个程序中,尾翼力和力矩是根据含有逆流原理或板块方法的细长体理论计算的。就子弹在有封闭舱室和敞开舱室母弹情况下的力和力矩而言,这两种方法的计算结果与风洞试验数据比较吻合。
In the study of the aerodynamic characteristics of the projectile near the projectile in the supersonic airflow, two bullet separation computer programs were used. The projectile interference flow fields in both programs are calculated based on the linearly varying source / sink and dipole distributions that represent the effects of volume and angle of attack, respectively. Considering the existence of arcuate shock in the bombshell, the calculated bombshell flow field contains a nonlinear correction. Use the equivalent flow field method to approach a bomblet with an open compartment. In order to get the load on the bullets, a lower and medium method of ranking is used. In a procedural low-level method, the projectile’s aerodynamic forces and moments are calculated using the slender body theory in the presence of a precursor elastic flow field. In another intermediate approach to the program, the bullets are modeled by a straight line singularity or slab method distributed over the projectile axis, integrating the surface pressure distribution to obtain the load on the bullet. This includes the effects of reflected shocks. In both programs, the wing forces and moments are calculated from the slender body theory that contains the counter-current principle or plate method. The calculated results of the two methods are in good agreement with the wind tunnel test data in terms of the force and moment of the bullet in a closed compartment and an open compartment projectile.